CN209988119U

CN209988119U - Solar flapping wing bionic aircraft

Info

Publication number: CN209988119U
Application number: CN201920509793.8U
Authority: CN
Inventors: 张志君; 陈默; 杨贺捷; 梁玉辉; 辛相锦
Original assignee: Jilin University
Current assignee: Jilin University
Priority date: 2019-04-16
Filing date: 2019-04-16
Publication date: 2020-01-24
Anticipated expiration: 2029-04-16

Abstract

A solar flapping wing bionic aircraft belongs to the technical field of aircrafts, and the flapping wing aircraft in the utility model adopts a miniature direct current motor connected with a secondary gear reducer to drive a flapping wing structure; the bionic flapping wing solar thin film wing plate provides a space for laying the flexible thin film solar cell panel; the empennage of the flapping wing aircraft is driven by two steering engines to rotate by cranks respectively, and the connecting rod is driven to swing so as to realize the rotation of the empennage in four directions, namely up-down direction, left-right direction. The utility model discloses can realize energy-conservation, high-efficient, sustainable of flapping wing aircraft, the structure and the motion of birds wing, fin simultaneously the utility model discloses a bionical flapping wing flight motion can embody, has that novel structure, drive mechanism are simple reliable, the energy can be palingenetic advantage.

Description

Solar flapping wing bionic aircraft

Technical Field

The utility model belongs to the technical field of the aircraft, concretely relates to solar energy flapping wing bionic aircraft.

Background

The flapping wing aircraft is designed to imitate the movement form of flapping wings of birds or insects, and has the functions of vertical take-off and landing, hovering, all-directional movement and the like. It not only has light weight and low cost, but also has simple structure and high efficiency. Therefore, the application prospect of the flapping wing aircraft in the national defense and civil fields is very wide, and the flapping wing aircraft has incomparable advantages when the flapping wing aircraft performs tasks in narrow space or complex terrain conditions.

Solar energy is a ubiquitous, simple and easily-obtained energy source in nature, and has the advantages of cleanness, environmental protection, renewability and the like. An important utilization form of solar energy is a solar photovoltaic power station, which mainly depends on a solar battery pack to form a component in series-parallel connection, and absorbed solar energy is converted into electric energy to be utilized.

There are three main types of solar cells currently occupying the mainstream, namely, single crystal silicon solar cells, polycrystalline silicon solar cells, and amorphous silicon solar cells. In recent years, as a second generation solar cell, the production development and application technology of a thin film solar cell are rapidly developed. The amorphous silicon thin-film solar cell in the thin-film solar cell has the advantages of less raw material consumption, low energy consumption in the manufacturing process, short energy repayment period and the like, the amorphous silicon thin-film solar cell panel can reach a light weight at present, the production cost is further reduced by the emerging organic thin-film solar cell, the dye sensitization technology and the like, the product has better flexibility, the wing shape of the flapping-wing aircraft can be well attached, and if the amorphous silicon thin-film solar cell can be applied to the micro flapping-wing aircraft, the flight performance of the flapping-wing aircraft can be greatly improved.

Disclosure of Invention

An object of the utility model is to provide a solar energy flapping wing bionic aircraft that novel structure, drive mechanism are simple reliable, the energy can be palingenetic.

The utility model discloses receive the inspiration of birds flight, provide a bionical solar energy flapping wing aircraft. The flapping wing aircraft is provided with a novel driving-transmission device mechanism, and has novel structure and simple and reliable transmission mechanism; and when the miniature aircraft flies, enough lifting force for flying is obtained through the bionic structures of the wing plates and the tail wings, and the flying requirements of the miniature aircraft are met. Meanwhile, the miniature aircraft also has flapping wings attached by the flexible solar thin-film battery panel, so that when the miniature aircraft flies, solar energy is converted into electric energy, energy compensation is realized, the flying is efficient and sustainable, and the miniature aircraft has important significance for improving the maneuverability and the cruising ability of the miniature aircraft with the flapping wings.

The utility model discloses constitute by solar energy film right wing board A, drive-transmission B, solar energy film left wing board C and bionical fin D, wherein: the solar film right wing plate A and the solar film left wing plate C are symmetrical structures about the central axis of the machine body a-a; a hole a of a right connecting rod 2 in the solar thin film right wing plate A is movably connected with a hole i on a limit rod pair a15 and a hole n on a rocker arm a12 in the driving-transmission device B; the hole b of the right connecting rod 2 is fixedly connected with the hole m of the rocker arm pair a12 through a bolt.

A hole a1 a1 of a left connecting rod 3 in a solar film left wing plate C is movably connected with a hole i1 i1 i1 on a limit rod pair B36 in a driving-transmission device B and a hole n1 n1 n 35 n rocker arm pair B; a hole b1 b1 of the left connecting rod 3 is fixedly connected with a hole m1 m1 on the rocker arm pair b35 through a bolt; the bionic tail D is hinged at the rear end of the body 1.

The q-slot q, the r-slot r and the s-slot s of the body 1 in the bionic tail D are fixedly connected with the fixing frame 20 of the driving-transmission device B through the o-hole o.

The solar charging controller 32 and the storage battery 33 of the driving-transmission device B are fixedly connected with the side frame 18; the solar charging controller 32 is in circuit connection with the solar cell panel 4 of the solar film right wing plate A and the solar film left wing plate C, one end of the storage battery 33 is connected with the solar charging controller 32, and the other end of the storage battery 33 is connected with the brushless motor 7 of the driving-transmission device B.

The solar film right wing plate A and the solar film left wing plate C are symmetrical structures about the central axis of the machine body a-a, have the same structure and opposite directions and are respectively composed of a solar cell panel 4, wing plates 5 and a framework 6, wherein the framework 6 is provided with a p hole p; the solar thin film right wing plate A is also provided with a right connecting rod 2, and the left end of the right connecting rod 2 is provided with a hole a and a hole b; the left wing plate C of the solar film is also provided with a left connecting rod 3, and the right end of the left connecting rod 3 is provided with a1 hole a1 and a b1 hole b 1; a framework 6 of a solar film left wing plate C is fixedly connected with the left connecting rod 3 through a hole p, and a wing plate 5 is supported by the framework 6; the solar panel 4 is adhered to the wing plate 5; the framework of the solar film right wing plate A is fixedly connected with the right connecting rod 2 through a hole p, and the wing plates are supported by the framework; the solar cell panel is adhered to the wing plate.

The driving-transmission device B is composed of a brushless motor 7, a right frame 8, a primary pinion 9, a primary gearwheel 10, a secondary pinion a11, a rocker arm pair a12, a yoke a13, a driving rod pair a14, a limiting rod pair a15, a secondary gearwheel a16, a bolt group a17, a side frame 18, a secondary pinion B19, a fixed frame 20, a left frame 21, a primary shaft 22, a secondary shaft 23, a secondary gearwheel B24, a yoke B34, a rocker arm pair B35, a limiting rod pair B36, a driving rod B37 and a bolt group B38, wherein: the right frame 8 and the left frame 21 are symmetrical structures about the central axis of the airframe a-a; the right frame 8 is provided with a hole c, a hole d, a hole e, a hole f, a hole g and a hole h; the left frame 21 is provided with a c1 hole c1, a d1 hole d1, an e1 hole e1, an f1 hole f1, a g1 hole g1 and an h1 hole h 1; the limiting rod pair a15 is provided with an i hole i; the rocker arm pair a12 is provided with a j hole j, a k hole k, an m hole m and an n hole n; the limiting rod pair b36 is provided with an i1 hole i 1; j1 holes j1, k1 holes k1, m1 holes m1 and n1 holes n1 are formed in the rocker arm pair b 35; the fixing frame 20 is provided with an o hole o; the right frame 8 and the left frame 21 are arranged in parallel and fixedly connected through the side frame 18; the brushless motor 7 is fixedly connected with the right frame 8 through a hole c, a hole d, a hole e and a hole f; the brushless motor 7 is fixedly connected with the left frame 21 through a c1 hole c1, a d1 hole d1, an e1 hole e1 and a f1 hole f 1; the primary pinion 9 is fixedly connected with the output end of the brushless motor 7; the primary shaft 22 and the secondary shaft 23 are arranged in parallel; a secondary pinion a11, a primary gearwheel 10 and a secondary pinion b19 are fixedly connected to the primary shaft 22 from right to left in sequence, and two ends of the primary shaft 22 are movably connected to a hole g of the right frame 8 and a hole g1 g1 of the left frame 21; a secondary gearwheel a16 and a secondary gearwheel b24 are fixedly arranged on the secondary shaft 23 in the front and back directions, and two ends of the secondary shaft 23 are movably connected to the h hole h of the right frame 8 and the h1 hole h1 of the left frame 21; the first-stage small gear 9 is meshed with the first-stage large gear 10; the secondary pinion a11 is meshed with the secondary bull gear a 16; the secondary pinion gear b19 meshes with the secondary bull gear b 24.

The limiting rod pair a15 is fixedly connected to the right side of the right frame 8; the n holes n on the rocker arm pair a12 are movably connected with the hole a of the connecting rod 1 and the hole i of the limiting rod pair a15 through a pin shaft; j holes j and k holes k on the rocker arm pair a12 are fixedly connected with two ends of a yoke a13 through a bolt group a 17; the driving rod a14 is fixedly connected with the tooth surface of the second-stage bull gear a 16; the yoke a13 has an elongated hole width greater than the diameter of the drive rod a 14.

The limiting rod pair b36 is fixedly connected to the left side of the left frame 21; n1 holes n1 on the rocker arm pair b35 are movably connected with a1 hole a1 of the connecting rod 1 and an i1 hole i1 of the limiting rod pair b36 through pin shafts; j1 holes j1 and k1 holes k1 on the rocker arm pair b35 are fixedly connected with the two ends of a yoke b34 through a bolt group b 38; the driving rod b37 is fixedly connected with the tooth surface of the second-stage bull gear a 16; the long hole width of the yoke b34 is larger than the diameter of the driving rod b 37; the bottom end of the fixed frame 20 is fixedly connected with the side frame 18.

Bionic tail D comprises fuselage 1, retaining ring 25, steering wheel 26, universal joint 27, horizontal tail 28, vertical tail 29, fixed plate 30 and articulated rope pair 31, wherein: a q-slot q, an r-slot r, an s-slot s, a t-slot t and a u-slot u are arranged on the machine body 3; the rear end of the machine body 1 is fixedly connected with the front of the universal joint 27; the universal joint 27 is hinged with the center of the fixing plate 30.

The hinge rope pair 31 consists of a left hinge rope and a right hinge rope, and the rear ends of the two hinge ropes are respectively fixedly connected with the left side and the right side of the fixing plate 30; the front ends of the two hinge ropes are fixedly connected with the left side and the right side of the steering engine 26 respectively.

The steering engine 26 is fixed on a t-shaped groove t and a u-shaped groove u of the machine body 1 through a check ring 25; the front ends of horizontal tail 28 and vertical tail 29 are fixed behind fixing plate 30.

The principle and the working process of the utility model are as follows:

in the utility model, the brushless motor 7 drives the first-level pinion 9 to rotate, through the meshing of the first-level pinion 9 and the first-level gearwheel 10, the second-level pinion a11, the axle center of the second-level pinion b19 is fixedly hinged, the second-level pinion a11 is meshed with the second-level gearwheel a16, the second-level pinion b19 is meshed with the second-level gearwheel b24, thereby driving the second-level gearwheel a16 and the second-level gearwheel b24 to rotate at the same rotating speed, the second-level gearwheel a16 and the second-level gearwheel b24 rotate to drive the driving rod a14 and the driving rod b37 on the respective gears to rotate around the gear center, meanwhile, the driving rod a14 slides in the long hole of the yoke a13, thereby driving the yoke a13 to move up and down, thereby realizing that the rocker pair a, finally, the right connecting rod 2 and the right wing plate A of the solar film, the left connecting rod 3 and the left wing plate C of the solar film are driven to flap up and down.

The flapping wing plate of the utility model consists of a wing plate 5, a solar cell panel 4, a brushless motor 7, a solar charging controller 32 and a storage battery 33; a plurality of amorphous silicon thin-film solar cell panels 4 laid on the wing plates 5 absorb solar energy, the storage battery 33 is protected through the solar charging controller 32, the electric energy converted by the solar energy is stably stored in the storage battery, the electric energy is stored in the storage battery 33, the passing motor is connected, energy is continuously supplemented for the brushless motor 7, and the sustainable and high efficiency of energy is realized.

The bionic tail wing D of the flapping wing aircraft is connected with the aircraft body 3 by adopting a spherical hinge auxiliary universal joint 27 to realize universal motion, and then the steering engine 26 pulls the hinge ropes 31 to respectively drive the rotation, so as to drive the fixed plate 30 to swing to realize the rotation of the horizontal tail wing 28 and the vertical tail wing 29 in four directions, namely up-down direction, left-right direction. The purpose of steering up and down and left and right can be realized by controlling the steering engine 26 to be matched with different steering directions. If steering engine 26 turns the same, horizontal tail wing 28 and vertical tail wing 29 can turn left and right. If the steering engine 26 is turned reversely, the flapping of the horizontal tail wing 28 and the vertical tail wing 29 can be realized, so that the ornithopter climbs or dives.

The beneficial effects of the utility model reside in that:

the utility model discloses receive the inspiration of birds flight, provide a bionical solar energy flapping wing aircraft. The flapping wing aircraft is provided with a novel driving-transmission device mechanism, and has novel structure and simple and reliable transmission mechanism; and when the miniature aircraft flies, enough lifting force for flying is obtained through the bionic structures of the wing plates and the tail wings, and the flying requirements of the miniature aircraft are met. Meanwhile, the miniature aircraft also has flapping wings attached by the flexible solar thin film battery panel, and when the miniature aircraft flies, solar energy is converted into electric energy to realize energy compensation, so that energy is saved, the flying capability is improved, the flying is efficient and sustainable, and the miniature aircraft has important significance for improving the maneuverability and the cruising capability of the miniature aircraft with the flapping wings.

The utility model discloses a flapping wing aircraft frame adopts ABS plastics to make, and connecting rod, rocker all adopt the nylon to make, and the axle is whole to adopt titanium alloy to make. The weight is light and meets certain strength conditions.

The utility model discloses a second grade expansion cylindrical gear reduction gear two-stage gear pairs the material the same, and it is plastics to detach axle and bearing outer used material to lighten the total weight as far as, each gear tooth width coefficient equals, makes flank of tooth contact strength approximately equal.

The utility model discloses from bionics, design bionical flapping wing structure, increase flight lift, reduce flight resistance, reduce the energy consumption when flying. In addition, a thin-film solar cell panel is bonded on a wing plate of the flapping-wing aircraft to supplement energy and power for the aircraft.

The utility model discloses a solar cell plate material adopt amorphous silicon thin-film solar cell, and the quality is lighter and can be crooked wantonly. The amorphous silicon thin-film solar cell panel has the characteristics of light weight and capability of generating power under weak light, makes up for short discharge plates of other solar cell panels under specific light sources, and then charges the battery, so that the cruising ability of the aircraft is enhanced to a certain extent.

Drawings

FIG. 1 is a schematic view of the overall structure of a solar flapping-wing bionic aircraft

FIG. 2 is an isometric view of a left and right solar film wing panel

FIG. 3 is a detail view of the right link

FIG. 4 is a detail view of the left link

FIG. 5 is a detail view of the skeleton

FIG. 6 is a detail view of the rocker arm pair a

FIG. 7 is a detail view of the rocker arm pair b

FIG. 8 is a right side view of the flapping wing aircraft drive-transmission configuration

FIG. 9 is an isometric view of a drive-transmission shaft and gear

FIG. 10 is an isometric view of the gantry

FIG. 11 is a left side view of the driving-transmission structure of the flapping wing aircraft

FIG. 12 is a schematic view of a gear transmission

FIG. 13 is a detail view of the right frame

FIG. 14 is a detail view of the left frame

FIG. 15 is a detail view of the stopper rod pair a

FIG. 16 is a detail view of the stopper rod pair b

FIG. 17 is a detail view of the fixing frame

FIG. 18 is a schematic diagram of the skeleton structure of a solar flapping-wing bionic aircraft

FIG. 19 is an isometric view of a tail assembly

FIG. 20 is an isometric view of a fuselage apparatus

FIG. 21 is a schematic view of the principle of solar thin film solar cell panel

Wherein: A. solar film right wing plate B, driving-transmission device C, solar film left wing plate D, bionic tail fin 1, machine body 2, right connecting rod 3, left connecting rod 4, solar panel 5, wing plate 6, framework 7, brushless motor 8, right frame 9, primary pinion 10, primary bull gear 11, secondary pinion a12, rocker arm pair a13, yoke a14, driving rod a15, limiting rod pair a16, secondary bull gear a17, bolt group a 18, side frame 19, secondary pinion b 20, fixed frame 21, left frame 22, primary shaft 23, secondary shaft 24, secondary bull gear b 25, retaining ring 26, steering gear 27, universal joint 28, horizontal tail fin 29, vertical tail fin 30, fixed plate 31, hinged rope pair 32, solar charging controller 33, storage battery 34, yoke b35, rocker arm pair b36, limiting rod pair b37, driving rod b38 Bolt group b

Detailed Description

The present invention will be described in detail with reference to the accompanying drawings:

as shown in fig. 1, the utility model discloses a by solar energy film right wing board A, drive-transmission B, solar energy film left wing board C and bionical fin D constitute, wherein: the solar film right wing plate A and the solar film left wing plate C are of symmetrical structures about the central axis of the machine body a-a; a hole a of a right connecting rod 2 in the solar thin film right wing plate A is movably connected with a hole i on a limit rod pair a15 and a hole n on a rocker arm a12 in the driving-transmission device B; the hole b of the right connecting rod 2 is fixedly connected with the hole m of the rocker arm pair a12 through a bolt.

As shown in fig. 2 to 5, the solar flapping wing bionic aircraft is characterized in that: the solar film right wing plate A and the solar film left wing plate C are symmetrical structures about the central axis of the machine body a-a, have the same structure and opposite directions and are respectively composed of a solar cell panel 4, wing plates 5 and a framework 6, wherein the framework 6 is provided with a p hole p; the solar thin film right wing plate A is also provided with a right connecting rod 2, and the left end of the right connecting rod 2 is provided with a hole a and a hole b; the left wing plate C of the solar film is also provided with a left connecting rod 3, and the right end of the left connecting rod 3 is provided with a hole a1 a1 and a hole b1 b 1.

A framework 6 of a solar film left wing plate C is fixedly connected with the left connecting rod 3 through a hole p, and a wing plate 5 is supported by the framework 6; the solar panel 4 is adhered to the wing plate 5; the framework of the solar film right wing plate A is fixedly connected with the right connecting rod 2 through a hole p, and the wing plates are supported by the framework; the solar cell panel is adhered to the wing plate.

As shown in fig. 6 to 14, the driving-transmission device B is composed of a brushless motor 7, a right frame 8, a primary pinion 9, a primary gearwheel 10, a secondary pinion a11, a rocker arm pair a12, a yoke a13, a driving lever pair a14, a limit lever pair a15, a secondary gearwheel a16, a bolt group a17, a side frame 18, a secondary pinion B19, a fixed frame 20, a left frame 21, a primary shaft 22, a secondary shaft 23, a secondary gearwheel B24, a yoke B34, a rocker arm pair B35, a limit lever pair B36, a driving lever B37 and a bolt group B38, wherein: the right frame 8 and the left frame 21 are symmetrical structures about the central axis of the airframe a-a; the right frame 8 is provided with a hole c, a hole d, a hole e, a hole f, a hole g and a hole h; the left frame 21 is provided with a c1 hole c1, a d1 hole d1, an e1 hole e1, an f1 hole f1, a g1 hole g1 and an h1 hole h 1; the limiting rod pair a15 is provided with an i hole i; the rocker arm pair a12 is provided with a j hole j, a k hole k, an m hole m and an n hole n; the limiting rod pair b36 is provided with an i1 hole i 1; j1 holes j1, k1 holes k1, m1 holes m1 and n1 holes n1 are formed in the rocker arm pair b 35; the fixing frame 20 is provided with an o hole o; the right frame 8 and the left frame 21 are arranged in parallel and fixedly connected through the side frame 18; the brushless motor 7 is fixedly connected with the right frame 8 through a hole c, a hole d, a hole e and a hole f; the brushless motor 7 is fixedly connected with the left frame 21 through a c1 hole c1, a d1 hole d1, an e1 hole e1 and a f1 hole f 1; the primary pinion 9 is fixedly connected with the output end of the brushless motor 7; the primary shaft 22 and the secondary shaft 23 are arranged in parallel; a secondary pinion a11, a primary gearwheel 10 and a secondary pinion b19 are fixedly connected to the primary shaft 22 from right to left in sequence, and two ends of the primary shaft 22 are movably connected to a hole g of the right frame 8 and a hole g1 g1 of the left frame 21; a secondary gearwheel a16 and a secondary gearwheel b24 are fixedly arranged on the secondary shaft 23 in the front and back directions, and two ends of the secondary shaft 23 are movably connected to the h hole h of the right frame 8 and the h1 hole h1 of the left frame 21; the first-stage small gear 9 is meshed with the first-stage large gear 10; the secondary pinion a11 is meshed with the secondary bull gear a 16; the secondary pinion gear b19 meshes with the secondary bull gear b 24.

As shown in fig. 15 to 17, the bionic tail D comprises a body 1, a retainer ring 25, a steering engine 26, a universal joint 27, a horizontal tail 28, a vertical tail 29, a fixing plate 30 and a pair of hinged ropes 31, wherein: a q-slot q, an r-slot r, an s-slot s, a t-slot t and a u-slot u are arranged on the machine body 3; the rear end of the machine body 1 is fixedly connected with the front of the universal joint 27; the universal joint 27 is hinged with the center of the fixing plate 30.

Claims

1. The utility model provides a solar energy flapping wing bionic aircraft which characterized in that: the solar energy film right wing plate (A), a driving-transmission device (B), a solar energy film left wing plate (C) and a bionic tail wing (D) form, wherein: the solar film right wing plate (A) and the solar film left wing plate (C) are symmetrical structures about the central axis of the fuselage a-a; a hole (a) of a right connecting rod (2) in a solar thin film right wing plate (A) is movably connected with an i hole (i) on a limiting rod pair a (15) in a driving-transmission device (B) and an n hole (n) on a rocker arm pair a (12); a hole b of the right connecting rod (2) is fixedly connected with a hole m of the rocker arm pair a (12) through a bolt; a hole a1 (a1) of a left connecting rod (3) in a solar film left wing plate (C) is movably connected with a hole i1 (i1) on a limiting rod pair B (36) in a driving-transmission device (B) and a hole n1 (n1) on a rocker arm pair B (35); a hole b1 (b1) of the left connecting rod (3) is fixedly connected with a hole m1 (m1) on the rocker arm pair b (35) through a bolt; the bionic tail wing (D) is hinged at the rear end of the body (1); a q groove (q), an r groove (r) and an s groove(s) of the body (1) in the bionic empennage (D) are fixedly connected with a fixing frame (20) of the driving-transmission device (B) through an o hole (o); a solar charging controller (32) and a storage battery (33) of the driving-transmission device (B) are fixedly connected with the side frame (18); the solar charging controller (32) is in circuit connection with the solar panel (4) of the solar film right wing plate (A) and the solar film left wing plate (C), one end of the storage battery (33) is connected with the solar charging controller (32), and the other end of the storage battery (33) is connected with the brushless motor (7) of the driving-transmission device (B).

2. A solar flapping wing bionic aircraft according to claim 1, wherein: the solar film right wing plate (A) and the solar film left wing plate (C) are symmetrical structures about the central axis of a-a of the machine body, have the same structure and opposite directions and are respectively composed of a solar cell panel (4), wing plates (5) and a framework (6), wherein the framework (6) is provided with a p hole (p); the solar thin film right wing plate (A) is also provided with a right connecting rod (2), and the left end of the right connecting rod (2) is provided with a hole (a) and a hole (b); the solar film left wing plate (C) is also provided with a left connecting rod (3), and the right end of the left connecting rod (3) is provided with a hole a1 (a1) and a hole b1 (b 1); a framework (6) of a solar film left wing plate (C) is fixedly connected with the left connecting rod (3) through a p hole (p), and a wing plate (5) is supported by the framework (6); the solar panel (4) is adhered to the wing plate (5); the framework of the solar thin film right wing plate (A) is fixedly connected with the right connecting rod (2) through a hole p, and the wing plate is supported by the framework; the solar cell panel is adhered to the wing plate.

3. A solar flapping wing bionic aircraft according to claim 1, wherein: drive-transmission (B) by brushless motor (7), right frame (8), one-level pinion (9), one-level gear wheel (10), second grade pinion a (11), the rocking arm is to a (12), yoke a (13), actuating lever a (14), the stop lever is to a (15), second grade gear wheel a (16), bolt group a (17), side frame (18), second grade pinion B (19), mount (20), left side frame (21), one-level axle (22), second grade axle (23), second grade gear wheel B (24), yoke B (34), the rocking arm is to B (35), the stop lever is to B (36), actuating lever B (37) and bolt group B (38) are constituteed, wherein: the right frame (8) and the left frame (21) are symmetrical structures about the central axis of the fuselage a-a; a hole (c), a hole (d), a hole (e), a hole (f), a hole (g) and a hole (h) are formed in the right frame (8); a c1 hole (c1), a d1 hole (d1), an e1 hole (e1), an f1 hole (f1), a g1 hole (g1) and an h1 hole (h1) are formed in the left frame (21); the limiting rod pair a (15) is provided with an i hole (i); j holes (j), k holes (k), m holes (m) and n holes (n) are formed in the rocker arm pair a (12); the limiting rod pair b (36) is provided with an i1 hole (i 1); a j1 hole (j1), a k1 hole (k1), an m1 hole (m1) and an n1 hole (n1) are formed in the rocker arm pair b (35); the fixing frame (20) is provided with an o hole (o); the right frame (8) and the left frame (21) are arranged in parallel and are fixedly connected through the side frame (18); the brushless motor (7) is fixedly connected with the right frame (8) through a hole c, a hole d, a hole e and a hole f; the brushless motor (7) is fixedly connected with the left frame (21) through a hole c1 (c1), a hole d1 (d1), a hole e1 (e1) and a hole f1 (f1) by bolts; the primary pinion (9) is fixedly connected with the output end of the brushless motor (7); the primary shaft (22) and the secondary shaft (23) are arranged in parallel; a secondary pinion a (11), a primary gearwheel (10) and a secondary pinion b (19) are fixedly connected to the primary shaft (22) from right to left in sequence, and two ends of the primary shaft (22) are movably connected to a hole g (g) of the right frame (8) and a hole g1 (g1) of the left frame (21); a secondary gearwheel a (16) and a secondary gearwheel b (24) are fixedly arranged on the secondary shaft (23) in the front and back directions, and two ends of the secondary shaft (23) are movably connected to a hole h (h) of the right rack (8) and a hole h1 (h1) of the left rack (21); the primary small gear (9) is meshed with the primary large gear (10); the secondary pinion a (11) is meshed with the secondary gearwheel a (16); the secondary small gear b (19) is meshed with the secondary big gear b (24); the limiting rod pair a (15) is fixedly connected to the right side of the right frame (8); the n holes (n) on the rocker arm pair a (12) are movably connected with the hole a (a) of the right connecting rod (2) and the hole i (i) of the limiting rod pair a (15) through a pin shaft; j holes (j) and k holes (k) on the rocker arm pair a (12) are fixedly connected with two ends of a yoke a (13) through a bolt group a (17); the driving rod a (14) is fixedly connected with the tooth surface of the second-stage gearwheel a (16); the width of the long hole of the yoke a (13) is larger than the diameter of the driving rod a (14); the limiting rod pair b (36) is fixedly connected to the left side of the left frame (21); an n1 hole (n1) on the rocker arm pair b (35) is movably connected with an a1 hole (a1) of the left connecting rod (3) and an i1 hole (i1) of the limiting rod pair b (36) through a pin shaft; a j1 hole (j1) and a k1 hole (k1) on the rocker arm pair b (35) are fixedly connected with the two ends of a yoke b (34) through a bolt group b (38); the driving rod b (37) is fixedly connected with the tooth surface of the second-stage gearwheel a (16); the long hole width of the yoke b (34) is larger than the diameter of the driving rod b (37); the bottom end of the fixed frame (20) is fixedly connected with the side frame (18).

4. A solar flapping wing bionic aircraft according to claim 1, wherein: bionic tail (D) comprises a body (1), a retainer ring (25), a steering engine (26), a universal joint (27), a horizontal tail (28), a vertical tail (29), a fixing plate (30) and a hinged rope pair (31), wherein: a q groove (q), an r groove (r), an s groove(s), a t groove (t) and a u groove (u) are arranged on the machine body (1); the rear end of the machine body (1) is fixedly connected with the front of the universal joint (27); the universal joint (27) is hinged with the center of the fixed plate (30); the hinge rope pair (31) consists of a left hinge rope and a right hinge rope, and the rear ends of the two hinge ropes are fixedly connected with the left side and the right side of the fixing plate (30) respectively; the front ends of the two hinge ropes are fixedly connected with the left side and the right side of the steering engine (26) respectively; the steering engine (26) is fixed on a t-shaped groove (t) and a u-shaped groove (u) of the machine body (1) through a check ring (25); the front ends of the horizontal tail wing (28) and the vertical tail wing (29) are fixedly connected with the back of the fixed plate (30).